Search Results for “Kondratiuk Ye. A.” – Collected book of scientific-technical articles

2.1.2020 Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems

Вацлав Самусевич

2. Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems

Authors:

Aksenenko A. V.¹, Hurskyi O. I.¹, Klochkov A. S.¹, Kondratiuk Ye. A.¹, Senkin V. S.², Siutkina-Doronina S. V.²

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine¹; The Institute of Technical Mechanics, Dnipro, Ukraine²

Page: Kosm. teh. Raket. vooruž. 2020, (1); 13-25

DOI: https://doi.org/10.33136/stma2020.01.013

Language: Russian

Annotation: The scientific and methodological propositions for the designing single-stage guided missiles with the solid rocket motors for advanced multiple launch rocket systems are defined. The guided missiles of multiple launch rocket system are intended for delivering munitions to the given spatial point with required and specified kinematic motion parameters at the end of flight. The aim of the article is an analysis of the development trends of the guided missiles with the solid rocket motors for the multiple launch rocket systems, identifying the characteristics and requirements for the flight trajectories, design parameters, control programs, overall dimensions and mass characteristics, structural layout and aerodynamic schemes of missiles. The formalization of the complex task to optimize design parameters, trajectory parameters and motion control programs for the guided missiles capable of flying along the ballistic, aeroballistic or combined trajectories is given. The complex task belongs to a problem of the optimal control theory with limitations in form of equa lity, inequality and differential constraints. To simplify the problem, an approach to program forming is proposed for motion control in the form of polynomial that brings the problem of the optimal control theory to a simpler problem of nonlinear mathematical programming. When trajectory parameters were calculated the missile was regarded as a material point of variable mass and the combined equations for center-of-mass motion of the guided missile with projections on axes of the terrestrial reference system were used. The structure of the mathematical model was given along with the calculation sequence of the criterion function that was used for determination of the optimal parameters, programs and characteristics. The mathematical model of the guided missile provides adequate accuracy for design study to determine depending on the main design parameters: overall dimensions and mass characteristics of the guided missile in general and its structural comp onents and subsystems; power, thrust and consumption characteristics of the rocket motor; aerodynamic and ballistic characteristics of the guided missile. The developed methodology was tested by determining design and trajectory parameters, overall dimensions and mass characteristics, power and ballistic characteristics of two guided missiles with wings for advanced multiple launch rocket systems produced by the People’s Republic of China, using the limited amount of information available in the product catalog.

Key words: multiple launch rocket systems (MLRS), complex problem of the optimal control theory, problem of nonlinear mathematical programming, main solid rocket motor, limitations for motion parameters and basic characteristics of the guided missiles

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3.1.2023 Analysis of a modernized 9K51 Hrad Multiple Rocket Launcher System to determine the performance specifications of the 122-mm unguided rocket projectile in development

manager — Fri, 12 May 2023 16:10:31 +0000

3. Analysis of a modernized 9K51 Hrad Multiple Rocket Launcher System to determine the performance specifications of the 122-mm unguided rocket projectile in development

Authors:

Aksenenko O. V., Hurskyi O. I., Klochkov A. S., Kondratiuk Ye. A., Shyniberov D. O.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2023 (1); 31-40

DOI: https://doi.org/10.33136/stma2023.01.031

Language: Ukrainian

Annotation: The article dwells on the multiple launch rocket systems with high firepower, firing rate and manoeuvrability, which continue to be one of the basic means of destruction of the land forces in the conditions of the modern armed conflicts. Authors observed the importance of reconstruction and upgrading of multiple launch rocket systems of Grad 9К51, Hurricane 9К57 and Tornado 9К58 types and missiles they use by the enterprises of the domestic military-industrial complex. The article dwells on the main areas of upgrading of the multiple launch rocket system Grad 9K51 performed by NPO Splav and co-operating enterprises in 1997‒1998 for a foreign customer. The key factors that allowed improving the performance of the Grad system in the upgrading process are identified in this article. The main characteristics of the unguided missiles 9M217, 9M218, 9M521, 9M522, designed for the foreign customer, had been investigated. The performance characteristics of the Tornado-G multiple launch rocket system which went into service with the Ministry of Defense of the Russian Federation in 2014, as well as the family of the upgraded unguided missiles 9M538, 9M539, 9M641, are analyzed. The article identifies the main areas of work for further improvement of the performance characteristics of the 122-mm unguided missile, developed by Yuzhnoe Design Office for the multiple launch rocket system 9K51 Grad. This article can be useful for the specialists in development of new and upgrading outdated systems of rocket weapons.

Key words: multiple launch rocket system (MLRS), missile, 9K51 Grad, 9M217, 9M218, 9M521, 9M522, Tornado-G, 9M538, 9M539, 9M541

Bibliography:

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